Induced drag given span efficiency factor Calculator

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✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%
✖Density of material is ratio of mass of material to its volume.ⓘ Density of Material [ρ]			+10% -10%
✖Velocity is a vector quantity (it has both magnitude and direction) and is the rate of change of the position of an object with respect to time.ⓘ Velocity [v]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S_ref]			+10% -10%

✖Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing.ⓘ Induced drag given span efficiency factor [D_i]

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Induced drag given span efficiency factor

Formula

`"D"_{"i"} = "C"_{"D"}*"ρ"*"v"^2*"S"_{"ref"}/2`

Example

`"30175.2N"="30"*"0.11kg/m³"*("60m/s")^2*"5.08m²"/2`

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Induced drag given span efficiency factor Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2
D_i = C_D*ρ*v^2*S_ref/2
This formula uses 5 Variables

Variables Used

Induced Drag - (Measured in Newton) - Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Density of Material - (Measured in Kilogram per Cubic Meter) - Density of material is ratio of mass of material to its volume.
Velocity - (Measured in Meter per Second) - Velocity is a vector quantity (it has both magnitude and direction) and is the rate of change of the position of an object with respect to time.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

STEP 1: Convert Input(s) to Base Unit

Drag Coefficient: 30 --> No Conversion Required
Density of Material: 0.11 Kilogram per Cubic Meter --> 0.11 Kilogram per Cubic Meter No Conversion Required
Velocity: 60 Meter per Second --> 60 Meter per Second No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

D_i = C_D*ρ*v^2*S_ref/2 --> 30*0.11*60^2*5.08/2

Evaluating ... ...

D_i = 30175.2

STEP 3: Convert Result to Output's Unit

30175.2 Newton --> No Conversion Required

FINAL ANSWER

30175.2 Newton <-- Induced Drag

(Calculation completed in 00.004 seconds)

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National Institute Of Technology (NIT), Hamirpur

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< 21 Lift and Drag Polar Calculators

Drag Coefficient for given zero-lift drag coefficient

Go Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Drag Coefficient for given parasite drag coefficient

Go Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Coefficient of Drag due to lift

Go Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)

Modern Lift Equation

Go Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2

Induced drag given span efficiency factor

Go Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2

Lift given induced drag

Go Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2)

Induced Drag for Wings having Elliptic Lift Distribution

Go Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral plane span^2)

Coefficient of lift given drag

Go Lift Coefficient = (Gross Weight*Drag Coefficient)/Drag Force

Coefficient of drag given drag

Go Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight

Drag

Go Drag Force = Gross Weight/Lift Coefficient/Drag Coefficient

Lift coefficient given drag coefficient

Go Lift Coefficient = Lift Force/Drag Force*Drag Coefficient

Drag coefficient given lift coefficient

Go Drag Coefficient = Lift Coefficient*Drag Force/Lift Force

Lift given drag coefficient

Go Lift Force = Lift Coefficient/Drag Coefficient*Drag Force

Drag given lift coefficient

Go Drag Force = Lift Force*Drag Coefficient/Lift Coefficient

Parasite Drag Coefficient at zero lift

Go Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift

Lift given lift coefficient

Go Lift Force = Lift Coefficient*Dynamic Pressure

Drag given drag coefficient

Go Drag Force = Drag Coefficient*Dynamic Pressure

Lift coefficient new

Go Lift Coefficient = Lift Force/Dynamic Pressure

Drag coefficient new

Go Drag Coefficient = Drag Force/Dynamic Pressure

Lift given aerodynamic force

Go Lift Force = Aerodynamic Force-Drag Force

Drag given aerodynamic force

Go Drag Force = Aerodynamic Force-Lift Force

Induced drag given span efficiency factor Formula

Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2
D_i = C_D*ρ*v^2*S_ref/2

What is the cause of induced drag?

Induced drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it.

How to Calculate Induced drag given span efficiency factor?

Induced drag given span efficiency factor calculator uses Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2 to calculate the Induced Drag, The Induced drag given span efficiency factor formula is defined as an inevitable consequence of lift and is produced by the passage of an aerofoil (e.g. wing or tailplane) through the air. Induced Drag is denoted by D_i symbol.

How to calculate Induced drag given span efficiency factor using this online calculator? To use this online calculator for Induced drag given span efficiency factor, enter Drag Coefficient (C_D), Density of Material (ρ), Velocity (v) & Reference Area (S_ref) and hit the calculate button. Here is how the Induced drag given span efficiency factor calculation can be explained with given input values -> 30175.2 = 30*0.11*60^2*5.08/2.

FAQ

What is Induced drag given span efficiency factor?

The Induced drag given span efficiency factor formula is defined as an inevitable consequence of lift and is produced by the passage of an aerofoil (e.g. wing or tailplane) through the air and is represented as D_i = C_D*ρ*v^2*S_ref/2 or Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2. Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, Density of material is ratio of mass of material to its volume, Velocity is a vector quantity (it has both magnitude and direction) and is the rate of change of the position of an object with respect to time & The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

How to calculate Induced drag given span efficiency factor?

The Induced drag given span efficiency factor formula is defined as an inevitable consequence of lift and is produced by the passage of an aerofoil (e.g. wing or tailplane) through the air is calculated using Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2. To calculate Induced drag given span efficiency factor, you need Drag Coefficient (C_D), Density of Material (ρ), Velocity (v) & Reference Area (S_ref). With our tool, you need to enter the respective value for Drag Coefficient, Density of Material, Velocity & Reference Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Induced Drag?

In this formula, Induced Drag uses Drag Coefficient, Density of Material, Velocity & Reference Area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral plane span^2)

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